38992 Federal Register / Vol. 80, No. 130 / Wednesday, July 8, 2015 / Proposed Rules 

Aircraft Industries GmbH, using the contact 

information in paragraph (h)(5) of this 

proposed AD. 

(5) For Technify Motors service 

information identified in this proposed AD, 

contact Technify Motors GmbH, 

Platanenstrasse 14, D–09356 Sankt Egidien, 

Germany; phone: +49–37204–696–0; fax: 

+49–37204–696–55; email: info@centurionengines.com. For DAI service information 

identified in this proposed AD, contact 

Diamond Aircraft Industries GmbH, N. A. 

Otto-Strasse 5, 2700 Wiener Neustadt, 

Austria; phone: +43 2622 26700; fax: +43 

2622 26700 1369; email: airworthiness@

diamond-air.at. 

(6) You may view this service information 

at the FAA, Engine & Propeller Directorate, 

12 New England Executive Park, Burlington, 

MA. For information on the availability of 

this material at the FAA, call 781–238–7125. 

Issued in Burlington, Massachusetts, on 

June 26, 2015. 

Ann C. Mollica, 

Acting Directorate Manager, Engine & 

Propeller Directorate, Aircraft Certification 

Service. 

[FR Doc. 2015–16586 Filed 7–7–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–2458; Directorate 

Identifier 2014–NM–122–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for all 

Airbus Model A318, A319, and A321 

series airplanes. This proposed AD was 

prompted by reports of in-flight loss of 

fixed and hinged main landing gear 

(MLG) fairings, and reports of postmodification MLG fixed fairing 

assemblies that have wear and 

corrosion. This proposed AD would 

require, for certain airplanes, repetitive 

replacements of the fixed fairing upper 

and lower attachment studs of both the 

right-hand (RH) and left-hand (LH) 

MLG; and repetitive inspections for 

corrosion, wear, fatigue, cracking, and 

loose studs of each forward stud 

assembly of the fixed fairing door upper 

and lower forward attachment of both 

RH and LH MLG; and replacement if 

necessary. This proposed AD also 

provides an optional terminating 

modification for the repetitive 

replacements of the fixed fairing upper 

and lower attachment studs. We are 

proposing this AD to prevent in-flight 

detachment of an MLG fixed fairing and 

consequent damage to the airplane. 

DATES: We must receive comments on 

this proposed AD by August 24, 2015. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed AD, contact Airbus, 

Airworthiness Office—EIAS, 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; telephone +33 5 61 93 36 

96; fax +33 5 61 93 44 51; email 

account.airworth-eas@airbus.com; 

Internet http://www.airbus.com. You 

may view this referenced service 

information at the FAA, Transport 

Airplane Directorate, 1601 Lind Avenue 

SW., Renton, WA. For information on 

the availability of this material at the 

FAA, call 425–227–1221. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

2458; or in person at the Docket 

Management Facility between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Operations 

office (telephone 800–647–5527) is in 

the ADDRESSES section. Comments will 

be available in the AD docket shortly 

after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone 425–227–1405; 

fax 425–227–1149. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2015–2458; Directorate Identifier 

2014–NM–122–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD based on those comments. 

We will post all comments we 

receive, without change, to http://

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2015–0001R1, dated January 

15, 2015 (referred to after this as the 

Mandatory Continuing Airworthiness 

Information, or ‘‘the MCAI’’), to correct 

an unsafe condition for all Model A318, 

A319, A320, and Model A321 series 

airplanes. The MCAI states: 

Several occurrences of in-flight loss of 

main landing gear (MLG) fixed and hinged 

fairings were reported. The majority of 

reported events occurred following 

scheduled maintenance activities. One result 

of the investigation was that a discrepancy 

between the drawing and the maintenance 

manuals was discovered. The maintenance 

documents were corrected to prevent misrigging of the MLG fixed and hinged fairings, 

which could induce fatigue cracking. 

Airbus issued Service Bulletin (SB) A320– 

52–1083, providing instructions for a onetime inspection of the MLG fixed fairing 

composite insert and the surrounding area, 

replacement of the adjustment studs at the 

lower forward position and adjustment to the 

new clearance tolerances. That SB was 

replaced by Airbus SB A320–52–1100 (mod 

27716) introducing a re-designed location 

stud, rod end and location plate at the 

forward upper and lower leg fixed-fairing 

positions. Subsequently, reports were 

received of post-mod 27716/post-SB A320– 

52–1100 MLG fixed fairing assemblies with 

corrosion, which could also induce cracking. 

This condition, if not detected and 

corrected, could lead to further cases of inflight detachment of a MLG fixed fairing, 

possibly resulting in injury to persons on the 

ground and/or damage to the aeroplane. 

To address this potential unsafe condition, 

EASA issued AD 2014-0096 [http://

ad.easa.europa.eu/blob/easa_ad_2014_0096_

superseded.pdf/AD_2014-0096_1] to require 

[for certain airplanes] repetitive detailed 

inspections (DET) of the MLG fixed fairings, 


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and, depending on findings, accomplishment 

of applicable corrective actions. That [EASA] 

AD also prohibited installation of certain 

MLG fixed fairing rod end assemblies and 

studs as replacement parts on aeroplanes 

incorporating Airbus mod 27716 in 

production, or modified in accordance with 

Airbus SB A320–52–1100 (any revision) in 

service. 

Since EASA AD 2014–0096 was issued, 

Airbus developed an alternative inspection 

programme to meet the AD requirements. In 

addition, a terminating action (mod 155648) 

was developed, which is to be made available 

for in service aeroplanes through Airbus SB 

A320–52–1165. 

For the reasons described above, this 

[EASA] AD retains the requirements of EASA 

AD 2014–0096, which is superseded, and 

adds an optional terminating action for the 

repetitive inspections. For post-mod 

aeroplanes, i.e. incorporating Airbus mod 

155648 in production, or modified by Airbus 

SB A320–52–1165 in service, the only 

remaining requirement is to ensure that premod components are no longer installed. 

Prompted by these developments, EASA 

issued AD 2015–0001, retaining the 

requirements of EASA AD 2014–0096, which 

was superseded, and adding an optional 

terminating action for the repetitive 

inspections. For post-mod aeroplanes, i.e. 

incorporating Airbus mod 155648 in 

production, or modified by Airbus SB A320– 

52–1165 in service, the only remaining 

requirement is to ensure that pre-mod 

components are no longer installed. 

Since that [EASA] AD was issued, it was 

discovered that a certain plate support, Part 

Number (P/N) D5285600620000 as listed in 

Table 3 of the [EASA] AD, remains part of 

the post SB A320–52–1165 configuration and 

is therefore not affected by any prohibition of 

installation—paragraph (11) of the [EASA] 

AD. In addition, an error was detected in 

Table 1 of the [EASA] AD (missing P/N plate 

support) and paragraph (9) was found to be 

incorrectly worded. 

For the reasons described above, this 

[EASA] AD is revised to introduce the 

necessary corrections. 

Required actions also include, for 

airplanes in Airbus pre-modification 

27716 and pre-Airbus Service Bulletin 

A320–52–1100 configuration on which 

certain components have been installed, 

repetitive replacements of the fixed 

fairing upper and lower attachment 

studs of both the RH and LH MLG. An 

optional terminating modification also 

is provided for the repetitive 

replacements of the fixed fairing upper 

and lower attachment studs. The 

optional terminating modification 

includes a resonance frequency 

inspection for debonding of the 

composite insert and delamination of 

the honeycomb area around the insert, 

and applicable corrective actions if 

necessary; and installation of new studs, 

rod ends, and location plates at the 

forward upper and lower leg fixedfairing positions. An additional optional 

terminating modification, for airplanes 

in pre-modification 27716 and preAirbus Service Bulletin A320–52–1100 

configuration, includes installation of a 

locking device, new studs, rod ends, 

and location plates at the forward upper 

and lower leg fixed-fairing positions. 

You may examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

2458. 

Related Service Information Under 1 

CFR Part 51 

• Airbus has issued Service Bulletin 

A320–52–1100, Revision 01, dated 

March 12, 1999. This service 

information describes procedures for 

modification of the airplane to postmodification 27716 configuration (by 

replacing the location stud, rod end, and 

location plate at the forward upper and 

lower leg fixed-fairing positions of the 

MLG door assemblies). The 

modification includes a resonance 

frequency inspection for debonding of 

the composite insert and delamination 

of the honeycomb area around the 

insert, and applicable corrective actions. 

Corrective actions include repairing the 

insert. The actions in this service 

information are an optional terminating 

modification. 

• Airbus has also issued Service 

Bulletin A320–52–1163, dated February 

4, 2014. This service information 

describes procedures for inspection of 

the fixed fairing forward attachments of 

the MLG door assemblies, and 

replacement of the fixed fairing upper 

and lower attachment studs of the RH 

and LH MLG door assemblies. 

• Airbus has issued Service Bulletin 

A320–52–1165, dated November 3, 

2014. This service information describes 

procedures for replacing the fairing 

attachment stud assemblies of the MLG 

door assembly with new assemblies. 

The actions in this service information 

are an optional terminating 

modification. 

This service information is reasonably 

available because the interested parties 

have access to it through their normal 

course of business or by the means 

identified in the ADDRESSES section of 

this AD. 

FAA’s Determination and Requirements 

of This Proposed AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all pertinent 

information and determined an unsafe 

condition exists and is likely to exist or 

develop on other products of these same 

type designs. 

Costs of Compliance 

We estimate that this proposed AD 

affects 851 airplanes of U.S. registry. 

We also estimate that it would take 

about 18 work-hours per product to 

comply with the basic inspection 

requirements of this proposed AD. The 

average labor rate is $85 per work-hour. 

Required parts would cost about $4,110 

per product. Based on these figures, we 

estimate the cost of this proposed AD on 

U.S. operators to be $4,799,640, or 

$5,640 per product. 

We estimate that the optional 

terminating modification would take 

about 18 work-hours and require parts 

costing $4,110, for a cost of $5,640 per 

product. 

In addition, we estimate that any 

necessary follow-on actions would take 

about 18 work-hours and require parts 

costing $4,110, for a cost of $5,640 per 

product. We have no way of 

determining the number of aircraft that 

might need these actions. 

According to the manufacturer, some 

of the costs of this proposed AD might 

be covered under warranty, thereby 

reducing the cost impact on affected 

individuals. We do not control warranty 

coverage for affected individuals. As a 

result, we have included all costs in our 

cost estimate. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this proposed AD 

would not have federalism implications 


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38994 Federal Register / Vol. 80, No. 130 / Wednesday, July 8, 2015 / Proposed Rules 

under Executive Order 13132. This 

proposed AD would not have a 

substantial direct effect on the States, on 

the relationship between the national 

Government and the States, or on the 

distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify this proposed regulation: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

2. Is not a ‘‘significant rule’’ under the 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); 

3. Will not affect intrastate aviation in 

Alaska; and 

4. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 14 CFR part 

39 as follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

Airbus: Docket No. FAA–2015–2458; 

Directorate Identifier 2014–NM–122–AD. 

(a) Comments Due Date 

We must receive comments by August 24, 

2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the Airbus airplanes 

identified in paragraphs (c)(1) through (c)(4) 

of this AD, certificated in any category, all 

manufacturer serial numbers. 

(1) Airbus Model A318–111, –112, –121, 

and –122 airplanes. 

(2) Airbus Model A319–111, –112, –113, 

–114, –115, –131, –132, and –133 airplanes. 

(3) Airbus Model A320–211, –212, –214, 

–231, –232, and –233 airplanes. 

(4) Airbus Model A321–111, –112, –131, 

–211, –212, –213, –231, and –232 airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 52, Doors. 

(e) Reason 

This AD was prompted by reports of inflight loss of fixed and hinged main landing 

gear (MLG) fairings, and reports of postmodification MLG fixed fairing assemblies 

that have wear and corrosion. We are issuing 

this AD to prevent in-flight detachment of an 

MLG fixed fairing and consequent damage to 

the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Repetitive Replacements 

For airplanes in pre-modification 27716 

and pre-Airbus Service Bulletin A320–52– 

1100 configuration, with any of the 

components installed that are identified in 

paragraphs (g)(1) through (g)(5) of this AD: At 

the applicable compliance time specified in 

paragraph (h) of this AD, replace fixed fairing 

upper and lower attachment studs of both 

right-hand (RH) and left-hand (LH) MLG, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

52–1163, dated February 4, 2014. Repeat the 

replacements thereafter at intervals not to 

exceed 6,500 flight cycles. 

(1) Plate—support having part number (P/ 

N) D5284024820000. 

(2) Plate—support having part number (P/ 

N) D5284024820200. 

(3) Stud—adjustment having P/N 

D5284024420000. 

(4) Rod end assembly (lower) having P/N 

D5284000500000. 

(5) Rod end assembly (upper) having P/N 

D5284000600000. 

(h) Compliance Times for the Requirements 

of Paragraph (g) of this AD 

Do the initial replacement required by 

paragraph (g) of this AD at the latest of the 

times specified in paragraphs (h)(1) through 

(h)(4) of this AD. 

(1) Before the accumulation of 6,500 total 

flight cycles since the airplane’s first flight. 

(2) Within 6,500 flight cycles since the last 

installation of a pre-modification 27716 stud 

on the airplane. 

(3) Within 1,500 flight cycles after the 

effective date of this AD. 

(4) Within 8 months after the effective date 

of this AD. 

(i) Repetitive Inspections 

For airplanes in post-modification 27716 or 

post-Airbus Service Bulletin A320–52–1100 

configuration, with any of the components 

installed that are identified in paragraphs 

(i)(1), (i)(2), and (i)(3) of this AD: At the 

applicable compliance time specified in 

paragraph (j) of this AD, do a detailed 

inspection of the LH and RH stud assemblies 

of the fixed fairing door upper and lower 

forward attachments of both RH and LH MLG 

for indications of corrosion, wear, fatigue, 

cracking, and loose studs, in accordance with 

the Accomplishment Instructions of Airbus 

Service Bulletin A320–52–1163, dated 

February 4, 2014. Repeat the inspection 

thereafter at intervals not to exceed 12 

months. Replacement of both RH and LH 

MLG forward stud assemblies on an airplane, 

in accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

52–1163, dated February 4, 2014, extends the 

interval for the next detailed inspection to 72 

months; and the inspection must be repeated 

thereafter at intervals not to exceed 12 

months. 

(1) Stud—adjustment having P/N 

D5285600720000. 

(2) Rod end assembly (lower) having P/N 

D5285600400000. 

(3) Rod end assembly (upper) having P/N 

D5285600500000. 

(j) Compliance Times for the Requirements 

of Paragraph (i) of This AD 

Do the initial inspection required by 

paragraph (i) of this AD at the latest of the 

times specified in paragraphs (j)(1) through 

(j)(4) of this AD. 

(1) Before the accumulation of 72 months 

since the airplane’s first flight. 

(2) Within 72 months since the last 

installation of a post-modification 27716 

assembly or since accomplishment of the 

actions specified in Airbus Service Bulletin 

A320–52–1100. 

(3) Within 1,500 flight cycles after the 

effective date of this AD. 

(4) Within 8 months after the effective date 

of this AD. 

(k) Corrective Action 

If any indication of corrosion, wear, 

fatigue, cracking, or loose studs of any 

forward stud assembly is found during any 

inspection required by paragraph (i) of this 

AD, except as specified in paragraph (l) of 

this AD: Before further flight, replace the 

upper and lower fixed fairing forward 

attachment assemblies of the RH and LH 

MLG, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–52–1163, dated 

February 4, 2014; or Airbus Service Bulletin 

A320–52–1165, dated November 3, 2014. 

(l) Corrective Action or Repetitive 

Inspections for Certain Corrosion Findings 

If any corrosion is found during any 

inspection required by paragraph (i) of this 

AD on any MLG fixed fairing forward 

attachment stud assembly (upper, lower, LH 

or RH), but the corroded stud is not loose: Do 

the action specified in paragraph (l)(1) or 

(l)(2) of this AD. 

(1) Before further flight, replace the 

affected assembly, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–52–1163, dated 

February 4, 2014; or Airbus Service Bulletin 

A320–52–1165, dated November 3, 2014. 

(2) Within 4 months after finding 

corrosion, and thereafter at intervals not to 

exceed 4 months, do a detailed inspection for 

indications of corrosion, wear, fatigue, 

cracking, and loose studs of the forward stud 

assembly of the affected (RH or LH) MLG, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

52–1163, dated February 4, 2014. 

(m) Corrective Action for Inspections 

Specified in Paragraph (l)(2) of This AD 

If any indication of wear, fatigue, cracking, 

or loose studs of any forward stud assembly 

is found during any inspection required by 


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paragraph (l)(2) of this AD: Before further 

flight, replace the affected (RH or LH) MLG 

fixed fairing forward attachment assembly, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

52–1163, dated February 4, 2014; or Airbus 

Service Bulletin A320–52–1165, dated 

November 3, 2014. 

(n) Terminating Action 

(1) Replacement of parts on an airplane, as 

required by paragraph (g), (k), or (l)(1) of this 

AD, does not constitute terminating action 

for the repetitive inspections required by 

paragraph (i) of this AD, except as specified 

in paragraph (n)(3) of this AD. 

(2) The repetitive replacements required by 

paragraph (g) of this AD may be terminated 

by modification of the airplane to postmodification 27716 configuration, including 

a resonance frequency inspection for 

debonding of the composite insert and 

delamination of the honeycomb area around 

the insert, and all applicable corrective 

actions, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–52–1100, Revision 01, 

dated March 12, 1999, provided all 

applicable corrective actions are done before 

further flight. Thereafter, refer to paragraph 

(i) of this AD to determine the compliance 

time for the next detailed inspection required 

by this AD. 

(3) Modification of an airplane, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

52–1165, dated November 3, 2014, 

constitutes terminating action for actions 

required by paragraphs (g) through (m) of this 

AD for the airplane on which the 

modification is done. 

(o) Exception to Certain AD Actions 

An airplane on which Airbus Modification 

155648 has been embodied in production is 

not affected by the requirements of 

paragraphs (g) and (i) of this AD, provided 

that no affected component, identified by 

part number as listed paragraphs (g)(1) 

through (g)(5) and (i)(1) through (i)(3) of this 

AD, has been installed on that airplane since 

first flight of the airplane. 

(p) Parts Installation Prohibition 

(1) For airplanes in pre-AirbusModification 27716 and pre-Airbus-ServiceBulletin A320–52–1100 configuration: No 

person may install a component identified in 

paragraphs (g)(1) through (g)(5) of this AD on 

any airplane after doing the actions provided 

in paragraph (n)(2) of this AD. 

(2) For airplanes in post-AirbusModification 27716 and post Airbus Service 

Bulletin A320–52–1100 configuration: As of 

the effective date of this AD, no person may 

install a component identified in paragraphs 

(g)(1) through (g)(5) of this AD on any 

airplane. 

(3) For airplanes in pre-AirbusModification 155648 and pre-Airbus-ServiceBulletin A320–52–1165 configuration: No 

person may install a component identified in 

paragraphs (g)(1) through (g)(5) and (i)(1) 

through (i)(3) of this AD on any airplane after 

doing the actions provided in paragraph 

(n)(3) of this AD. 

(4) For airplanes in post-AirbusModification 155648 and post-AirbusService-Bulletin A320–52–1165 

configuration: As of the effective date of this 

AD, no person may install a component 

identified in (g)(1) through (g)(5) and (i)(1) 

through (i)(3) of this AD on any airplane. 

(q) Credit for Previous Actions 

This paragraph provides credit for optional 

actions provided by paragraph (n)(2) of this 

AD, if those actions were performed before 

the effective date of this AD using Airbus 

Service Bulletin A320–52–1100, dated 

December 7, 1998, which is not incorporated 

by reference in this AD. 

(r) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

In accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the International Branch, send it to ATTN: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1405; fax 425–227–1149. 

Information may be emailed to: 9-ANM-116- 

AMOC-REQUESTS@faa.gov. Before using 

any approved AMOC, notify your appropriate 

principal inspector, or lacking a principal 

inspector, the manager of the local flight 

standards district office/certificate holding 

district office. The AMOC approval letter 

must specifically reference this AD. 

(2) Contacting the Manufacturer: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer, the action must 

be accomplished using a method approved 

by the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

the European Aviation Safety Agency 

(EASA); or Airbus’s EASA Design 

Organization Approval (DOA). If approved by 

the DOA, the approval must include the 

DOA-authorized signature. 

(s) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2015–0001R1, dated 

January 15, 2015, for related information. 

This MCAI may be found in the AD docket 

on the Internet at http://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2015–2458. 

(2) For service information identified in 

this AD, contact Airbus, Airworthiness 

Office—EIAS, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France; 

telephone +33 5 61 93 36 96; fax +33 5 61 

93 44 51; email account.airworth-eas@

airbus.com; Internet http://www.airbus.com. 

You may view this service information at the 

FAA, Transport Airplane Directorate, 1601 

Lind Avenue SW., Renton, WA. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 

Issued in Renton, Washington, on June 30, 

2015. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–16583 Filed 7–7–15; 8:45 am] 

BILLING CODE 4910–13–P 

SECURITIES AND EXCHANGE 

COMMISSION 

17 CFR Part 240 

[Release No. 33–9862; 34–75344 File No. 

S7–13–15] 

RIN 3235–AL70 

Possible Revisions To Audit 

Committee Disclosures 

AGENCY: Securities and Exchange 

Commission. 

ACTION: Concept release; request for 

comments. 

SUMMARY: The Commission is 

publishing this concept release to seek 

public comment regarding audit 

committee reporting requirements, with 

a focus on the audit committee’s 

reporting of its responsibilities with 

respect to its oversight of the 

independent auditor. Some have 

expressed a view that the Commission’s 

disclosure rules for this area may not 

result in disclosures about audit 

committees and their activities that are 

sufficient to help investors understand 

and evaluate audit committee 

performance, which may in turn inform 

those investors’ investment or voting 

decisions. The majority of these 

disclosure requirements, which exist in 

their current form principally in Item 

407 of Regulation S–K, were adopted in 

1999. Since then, there have been 

significant changes in the role and 

responsibilities of audit committees 

arising out of, among other things, the 

Sarbanes-Oxley Act of 2002, enhanced 

listing requirements for audit 

committees, enhanced requirements for 

auditor communications with the audit 

committee arising out of the rules of the 

Public Company Accounting Oversight 

Board, and changes in practice, both 

domestically and internationally. 

DATES: Comments should be received on 

or before September 8, 2015. 

ADDRESSES: Comments may be 

submitted by any of the following 

methods: 

Electronic Comments 

• Use the Commission’s Internet 

comment form (http://www.sec.gov/

rules/concept.shtml); or 


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